CN211281490U

CN211281490U - Unmanned aerial vehicle of aerial transmission and recovery

Info

Publication number: CN211281490U
Application number: CN201922257819.7U
Authority: CN
Inventors: 刘艳军; 罗竑; 梁斌; 吴海杰; 林玉祥
Original assignee: Universal Star Suzhou Co ltd
Current assignee: Universal Star Suzhou Co ltd
Priority date: 2019-12-16
Filing date: 2019-12-16
Publication date: 2020-08-18
Anticipated expiration: 2029-12-16

Abstract

The utility model relates to a general aviation field, concretely relates to unmanned aerial vehicle of aerial transmission and recovery. Including fuselage, wing, fin, driving system and vertical fin, fuselage internal integration flight control system, electromechanical system and avionics system, fuselage front end horizontal symmetry installs the wing and forms right wing and left wing, the right wing with left wing can to the fuselage is rotatory or folding to be accomodate, and is hidden fuselage inside or lower part, fuselage tail end horizontal symmetry installs the fin forms left fin and right fin, left fin with right fin all can be folded down. The utility model discloses the fuselage is inside or the lower extreme is accomodate in the wing is rotatable or folding, and the fin design is collapsible simultaneously, can significantly reduce unmanned aerial vehicle and load required space, provides the advantage for the aerial transmission of unmanned aerial vehicle cluster and recovery.

Description

Unmanned aerial vehicle of aerial transmission and recovery

Technical Field

The utility model relates to a general aviation field, concretely relates to unmanned aerial vehicle of aerial transmission and recovery.

Background

The national institute and colleges have developed the preliminary study of the "unmanned aerial vehicle cluster" distributed combat concept, wherein the unmanned aerial vehicles participating in the cluster networking can be launched in the modes of ejection, barrel shooting and the like. However, at present, corresponding research is not carried out on the research aspect of the small unmanned aerial vehicle capable of being launched and recovered in the air.

SUMMERY OF THE UTILITY MODEL

The utility model provides a technical problem provide an unmanned aerial vehicle who possesses collapsible, but quick assembly disassembly, carry the space little, can launch aloft and retrieve aloft.

The utility model provides a technical scheme that its technical problem adopted is:

the utility model provides an unmanned aerial vehicle of aerial emission and recovery, includes fuselage, wing, fin, driving system and vertical fin, the inside integrated flight control system of fuselage, electromechanical system and navigation system, fuselage front end horizontal symmetry installs the wing and forms right wing and left wing, the right wing with left wing can to the fuselage is rotatory or folding to be accomodate, and hide inside or the lower part of fuselage, fuselage tail end horizontal symmetry installs the fin forms left fin and right fin, left side fin with the right fin all can be folded down, fuselage tail end lower surface installs perpendicularly the vertical fin, driving system hides to be installed inside the fuselage tail end, the fuselage upper surface is provided with air inlet unit, air inlet unit does driving system provides mobile gas.

Further, the surface of the body is provided with an antenna.

Further, the right wing and the left wing are symmetrically provided with a right aileron and a left aileron.

Further, the width of the right wing and the left wing after being rotated or folded is smaller than that of the fuselage.

Further, the tail is a V-shaped tail.

Further, the V-shaped empennage is a downward-reverse-angle V-shaped empennage.

Furthermore, the left empennage and the right empennage are symmetrically provided with elevators.

Further, the air inlet devices are symmetrically arranged on the upper surface of the machine body.

Further, the fuselage adopts a lifting body fuselage appearance.

The utility model has the advantages that:

the wing can be rotated or folded to be accommodated in the fuselage or at the lower end, and meanwhile, the tail wing is foldable, so that the space required by the unmanned aerial vehicle can be greatly reduced, and favorable conditions are provided for the aerial launching and recovery of the unmanned aerial vehicle cluster.

Drawings

FIG. 1 is a three-dimensional structure of the present invention;

FIG. 2 is a folded deformation view of FIG. 1;

labeled as:

1. fuselage, 2, right wing, 3, left wing, 4, empennage, 5, power system, 6, vertical fin, 11, antenna, 12, air inlet unit, 21, right aileron, 31, left aileron, 41, elevator.

Detailed Description

In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below. In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. This invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein.

It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present.

Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.

An unmanned aerial vehicle for air launching and recovery is shown in figure 1 and comprises a body 1, wings, a tail wing 4, a power system 5 and a vertical fin 6, a flight control system, an electromechanical system and a navigation system are integrated in the body 1, the front end of the body 1 is horizontally and symmetrically provided with the wings to form a right wing 2 and a left wing 3, the right wing 2 and the left wing 3 can be rotated or folded to be stored in the body 1 and hidden in the inner part or the lower part of the body 1, after the rotation or folding storage, the tail end of the body 1 is shown in figure 2, the tail wing 4 is horizontally and symmetrically provided with the tail wing to form a left tail wing and a right tail wing, the left tail wing and the right tail wing can be folded downwards, after the folding, the vertical fin 6 is vertically arranged on the lower surface of the tail end of the body 1, the power system 5 is hidden in the inner part of the tail end of the body, hidden in the tail end of the machine body 1, and air is fed through an air inlet device 12 at the upper part of the tail end of the machine body.

An antenna 11 for receiving and transmitting signals is arranged on the surface of the fuselage 1, a right aileron 21 and a left aileron 31 are symmetrically arranged on the right wing 2 and the left wing 3, and the width of the right wing 2 and the left wing 3 after rotating or folding towards the interior of the fuselage 1 is smaller than that of the fuselage 1.

The empennage 4 adopts a V-shaped empennage with a downward dihedral angle, and elevators 41 are symmetrically arranged on the empennage 4, so that the empennage 4 can be folded downwards for storage.

The air inlet device 12 adopts a symmetrical component, is symmetrically arranged on the upper surface of the machine body 1 and provides flowing air for the power system 5. The fuselage 1 adopts the shape of a lifting body fuselage.

As shown in fig. 2, the right wing 2 and the left wing 3 rotate inwards or are folded for storage, and the tail wing 4 is folded downwards, so that the space required by the unmanned aerial vehicle loading can be greatly reduced, and favorable conditions are provided for the aerial launching and recovery of the unmanned aerial vehicle cluster.

The length of the fuselage 1 is 1.5m, the width is 0.22m, the height is 0.11m, the wing span is 1.24m, the chord length is 0.105m, the width of the folded left wing and the folded right wing is 0.216m, the width is smaller than the fuselage width, and the folded left wing and the folded right wing can be hidden in the wing folding space. The tail wing 4 is an inverted V-shaped tail, the length of a single wing is 0.35m, the down-dihedral angle is 15 degrees, and the width of the whole folded tail wing is kept at 0.34 m. Through folding design, the occupation space of aerial transmission of reduction that can be great and recovery unmanned aerial vehicle makes it more practical.

The above-mentioned embodiments, further detailed description of the objects, technical solutions and advantages of the present invention, it should be understood that the above-mentioned embodiments are only specific embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the scope of the present invention.

Claims

1. The utility model provides an unmanned aerial vehicle of aerial transmission and recovery which characterized in that: including fuselage (1), wing, fin (4), driving system (5) and vertical fin (6), fuselage (1) internal integration flight control system, electromechanical system and navigation system, fuselage (1) front end horizontal symmetry installs the wing and forms right wing (2) and left wing (3), right wing (2) with left wing (3) can to fuselage (1) is rotatory or folding accomodate to hide in fuselage (1) inside or lower part, fuselage (1) tail end horizontal symmetry installs fin (4) form left fin and right fin, left fin with right fin all can fold down, fuselage (1) tail end lower surface is installed perpendicularly vertical fin (6), driving system (5) are hidden and are installed inside fuselage (1) tail end, fuselage (1) upper surface is provided with air inlet unit (12), the air inlet device (12) provides flowing air for the power system (5).

2. An aerial launch and recovery drone as claimed in claim 1, characterised in that: the surface of the machine body (1) is provided with an antenna (11).

3. An aerial launch and recovery drone as claimed in claim 2, characterised in that: the right wing (2) and the left wing (3) are symmetrically provided with a right aileron (21) and a left aileron (31).

4. An aerial launch and recovery drone as claimed in claim 3, characterised in that: the right wing (2) and the left wing (3) are high-lift airfoil wings.

5. An aerial launch and recovery drone as claimed in claim 4, characterised in that: the width of the right wing (2) and the left wing (3) after being rotated or folded is smaller than that of the fuselage (1).

6. An aerial launch and recovery drone according to any one of claims 1 to 5, characterised in that: the tail wing (4) is a V-shaped tail wing.

7. An aerial launch and recovery drone as claimed in claim 6, characterised in that: the V-shaped empennage is a V-shaped empennage with a downward reverse angle.

8. An aerial launch and recovery drone as claimed in claim 7, wherein: the left and right empennages are symmetrically provided with elevators (41).

9. An aerial launch and recovery drone as claimed in claim 8, wherein: the air inlet devices (12) are symmetrically arranged on the upper surface of the machine body (1).

10. An aerial launch and recovery drone as claimed in claim 1, characterised in that: the machine body (1) adopts the shape of a lifting body.